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FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 61-163 AIRFOIL (fx61163-il)
Reynolds number: 200,000
Max Cl/Cd: 70.86 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61163-il-200000.txt
Download as CSV file: xf-fx61163-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-163 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2875   0.10693   0.10379  -0.0507   1.0001   0.0544
 -11.500  -0.3082   0.10006   0.09696  -0.0556   1.0001   0.0549
 -11.250  -0.3298   0.09282   0.08973  -0.0601   1.0001   0.0550
 -11.000  -0.3123   0.09061   0.08761  -0.0556   1.0001   0.0568
 -10.750  -0.3030   0.08888   0.08592  -0.0540   1.0001   0.0582
 -10.500  -0.3046   0.08517   0.08225  -0.0543   1.0001   0.0595
 -10.250  -0.3133   0.08009   0.07722  -0.0558   1.0001   0.0610
 -10.000  -0.3366   0.07212   0.06930  -0.0597   1.0001   0.0616
  -9.750  -0.3732   0.06423   0.06141  -0.0634   1.0001   0.0608
  -7.750  -0.4018   0.03226   0.02583  -0.0917   0.8851   0.0335
  -7.500  -0.3668   0.03038   0.02356  -0.0935   0.8629   0.0332
  -7.250  -0.3382   0.02673   0.01968  -0.0938   0.8453   0.0314
  -7.000  -0.3115   0.02459   0.01724  -0.0933   0.8297   0.0304
  -6.750  -0.2858   0.02302   0.01543  -0.0925   0.8163   0.0299
  -6.500  -0.2607   0.02180   0.01404  -0.0915   0.8049   0.0300
  -6.250  -0.2360   0.02080   0.01291  -0.0905   0.7953   0.0305
  -6.000  -0.2128   0.01995   0.01199  -0.0895   0.7855   0.0315
  -5.750  -0.1892   0.01924   0.01119  -0.0889   0.7770   0.0326
  -5.500  -0.1686   0.01806   0.00998  -0.0886   0.7693   0.0356
  -5.250  -0.1439   0.01741   0.00929  -0.0889   0.7624   0.0409
  -5.000  -0.1188   0.01643   0.00822  -0.0896   0.7556   0.0493
  -4.750  -0.0917   0.01251   0.00657  -0.0949   0.7497   0.5062
  -4.500  -0.0657   0.01317   0.00740  -0.0935   0.7431   0.5866
  -4.250  -0.0409   0.01456   0.00872  -0.0911   0.7380   0.6227
  -4.000  -0.0185   0.01600   0.01013  -0.0881   0.7326   0.6435
  -3.750   0.0042   0.01712   0.01121  -0.0853   0.7271   0.6572
  -3.500   0.0239   0.01824   0.01228  -0.0813   0.7226   0.6623
  -3.250   0.0521   0.01835   0.01227  -0.0817   0.7175   0.6727
  -3.000   0.0760   0.01860   0.01245  -0.0802   0.7125   0.6754
  -2.750   0.1028   0.01871   0.01244  -0.0798   0.7082   0.6794
  -2.500   0.1343   0.01847   0.01205  -0.0817   0.7038   0.6876
  -2.250   0.1578   0.01864   0.01220  -0.0803   0.6989   0.6902
  -2.000   0.1839   0.01874   0.01222  -0.0798   0.6948   0.6944
  -1.750   0.2171   0.01857   0.01187  -0.0819   0.6911   0.7022
  -1.500   0.2400   0.01866   0.01198  -0.0806   0.6862   0.7046
  -1.250   0.2657   0.01871   0.01199  -0.0801   0.6816   0.7082
  -1.000   0.2985   0.01857   0.01171  -0.0820   0.6776   0.7150
  -0.750   0.3241   0.01858   0.01171  -0.0816   0.6731   0.7184
  -0.500   0.3484   0.01864   0.01177  -0.0808   0.6681   0.7214
  -0.250   0.3767   0.01863   0.01169  -0.0812   0.6640   0.7256
   0.000   0.4112   0.01852   0.01146  -0.0835   0.6604   0.7316
   0.250   0.4340   0.01857   0.01157  -0.0825   0.6555   0.7339
   0.500   0.4601   0.01859   0.01159  -0.0822   0.6510   0.7369
   0.750   0.4899   0.01859   0.01152  -0.0830   0.6473   0.7411
   1.000   0.5228   0.01855   0.01145  -0.0850   0.6427   0.7463
   1.250   0.5466   0.01857   0.01153  -0.0842   0.6377   0.7484
   1.500   0.5732   0.01859   0.01152  -0.0839   0.6334   0.7514
   1.750   0.6019   0.01864   0.01155  -0.0844   0.6289   0.7552
   2.000   0.6343   0.01861   0.01155  -0.0863   0.6230   0.7599
   2.250   0.6608   0.01860   0.01153  -0.0861   0.6186   0.7625
   2.500   0.6872   0.01868   0.01160  -0.0858   0.6147   0.7652
   2.750   0.7126   0.01875   0.01178  -0.0857   0.6088   0.7684
   3.000   0.7437   0.01874   0.01176  -0.0868   0.6040   0.7721
   3.250   0.7772   0.01878   0.01174  -0.0885   0.5998   0.7759
   3.500   0.7992   0.01885   0.01195  -0.0875   0.5935   0.7783
   3.750   0.8267   0.01884   0.01197  -0.0875   0.5885   0.7809
   4.000   0.8554   0.01888   0.01202  -0.0880   0.5832   0.7839
   4.250   0.8845   0.01889   0.01211  -0.0888   0.5762   0.7876
   4.500   0.9172   0.01885   0.01205  -0.0901   0.5714   0.7908
   4.750   0.9402   0.01894   0.01228  -0.0893   0.5648   0.7931
   5.000   0.9675   0.01889   0.01227  -0.0894   0.5587   0.7956
   5.250   0.9951   0.01887   0.01231  -0.0895   0.5518   0.7986
   5.500   1.0243   0.01881   0.01231  -0.0901   0.5444   0.8020
   5.750   1.0553   0.01880   0.01234  -0.0912   0.5375   0.8051
   6.000   1.0798   0.01869   0.01233  -0.0906   0.5294   0.8073
   6.250   1.1050   0.01863   0.01235  -0.0902   0.5214   0.8100
   6.500   1.1320   0.01855   0.01234  -0.0902   0.5135   0.8131
   6.750   1.1585   0.01851   0.01240  -0.0903   0.5035   0.8162
   7.000   1.1877   0.01838   0.01232  -0.0909   0.4926   0.8192
   7.250   1.2118   0.01825   0.01223  -0.0902   0.4824   0.8217
   7.500   1.2341   0.01828   0.01241  -0.0894   0.4708   0.8245
   7.750   1.2581   0.01833   0.01257  -0.0889   0.4590   0.8273
   8.000   1.2830   0.01844   0.01274  -0.0887   0.4467   0.8303
   8.250   1.3080   0.01858   0.01296  -0.0887   0.4318   0.8336
   8.500   1.3279   0.01874   0.01316  -0.0875   0.4152   0.8363
   8.750   1.3459   0.01900   0.01342  -0.0860   0.3962   0.8390
   9.000   1.3629   0.01938   0.01383  -0.0846   0.3748   0.8419
   9.250   1.3785   0.01991   0.01433  -0.0830   0.3521   0.8452
   9.750   1.3998   0.02126   0.01568  -0.0786   0.3036   0.8518
  10.000   1.4020   0.02223   0.01658  -0.0752   0.2774   0.8551
  10.250   1.4046   0.02351   0.01779  -0.0725   0.2481   0.8587
  10.500   1.4043   0.02519   0.01936  -0.0700   0.2204   0.8626
  10.750   1.4018   0.02699   0.02112  -0.0675   0.1953   0.8663
  11.000   1.3978   0.02917   0.02325  -0.0654   0.1750   0.8704
  11.250   1.3960   0.03157   0.02564  -0.0642   0.1553   0.8747
  11.500   1.3924   0.03436   0.02838  -0.0634   0.1374   0.8787
  11.750   1.3875   0.03717   0.03119  -0.0623   0.1212   0.8826
  12.000   1.3833   0.04013   0.03415  -0.0616   0.1051   0.8872
  12.250   1.3782   0.04336   0.03736  -0.0612   0.0907   0.8920
  12.500   1.3712   0.04651   0.04052  -0.0604   0.0790   0.8971
  12.750   1.3640   0.04985   0.04389  -0.0598   0.0690   0.9030
  13.000   1.3548   0.05341   0.04745  -0.0592   0.0611   0.9091
  13.250   1.3490   0.05656   0.05069  -0.0586   0.0542   0.9164
  13.500   1.3376   0.06041   0.05455  -0.0581   0.0491   0.9248
  13.750   1.3346   0.06310   0.05740  -0.0573   0.0434   0.9392
  14.000   1.3223   0.06648   0.06083  -0.0564   0.0397   0.9999
  14.250   1.3205   0.07039   0.06482  -0.0575   0.0337   0.9999
  14.500   1.3101   0.07540   0.06982  -0.0588   0.0291   0.9999
  14.750   1.3040   0.07999   0.07450  -0.0600   0.0249   0.9999
  15.000   1.2889   0.08569   0.08022  -0.0614   0.0223   0.9999
  15.250   1.2857   0.08997   0.08463  -0.0626   0.0199   0.9999
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